EP0037897A1 - Dispositif de refroidissement interne d'une turbine à gaz - Google Patents

Dispositif de refroidissement interne d'une turbine à gaz Download PDF

Info

Publication number
EP0037897A1
EP0037897A1 EP81101560A EP81101560A EP0037897A1 EP 0037897 A1 EP0037897 A1 EP 0037897A1 EP 81101560 A EP81101560 A EP 81101560A EP 81101560 A EP81101560 A EP 81101560A EP 0037897 A1 EP0037897 A1 EP 0037897A1
Authority
EP
European Patent Office
Prior art keywords
angle
channel
gas turbine
degrees
cooling
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP81101560A
Other languages
German (de)
English (en)
Inventor
Edmund Owsianny
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of EP0037897A1 publication Critical patent/EP0037897A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • the invention relates to a device for cooling the interior of a gas turbine, in which an inlet channel supplies cooling gas between two labyrinth seals.
  • a device for cooling a gas turbine is described in DE-OS 2 218 705. It has a valve housing which is arranged for rotation with the engine shaft. The walls of the housing form an annular air chamber, which is sealed with two labyrinth seals. The cooling gas is supplied between the labyrinth seals.
  • the cooling gas is to be conveyed by the rotation of the turbine.
  • a buffer channel is present, in or from the a 'sentlichen essen- axial supply and discharge of cooling gas by the entry channel and through an exit channel.
  • the flow of the cooling gas is advantageously supported by the fact that the inlet channel within a cylinder jacket concentric to the axis of rotation of the gas turbine is inclined by an angle ⁇ in the direction of rotation relative to a generator of the cylinder jacket and the outlet channel is inclined relative to the generating channel by an angle P against the direction of rotation.
  • the angle ⁇ advantageously has a size of 0 to 60 degrees and the angle ⁇ of 0 to 60 degrees.
  • a size of the angles ⁇ and ⁇ of 15 to 60 degrees is particularly advantageous.
  • a promotion of the cooling gas by centrifugal force is advantageously achieved in that the outlet channel opens into a buffer space which is connected to the attachment space of the blade root by a bore and that the bore is inclined by an angle ⁇ with respect to the axis of rotation.
  • the angle ⁇ advantageously has a size of 15 to 90 degrees.
  • the gas turbine consists of a rotor 1 and a stator 2.
  • the cooling gas is guided through an inlet duct 4 into a buffer duct 3, which is sealed between the rotor 1 and the stator 2 by two labyrinth seals 10 and 11.
  • the cooling gas is discharged through an outlet channel 5.
  • the inlet channel 4 is inclined within an cylinder jacket concentric to the plane of rotation by an angle o in the running direction with respect to a generator of the cylinder jacket.
  • the outlet channel 5 is inclined at an angle to the generatrix against the running direction.
  • the outlet channel 5 opens into a buffer space 6 which is connected to the fastening space 8 of the blade root 9 by a bore 7.
  • This bore 7 is inclined at an angle ⁇ with respect to the axis of rotation in order to achieve conveying of the cooling gas by centrifugal force.
  • the device according to the invention offers an excellent cooling gas flow. Characterized in that the cooling gas is conveyed by the rotation of the turbine due to the arrangement of the inlet channel 4, the outlet channel 5 and the bore 7, it is achieved that the cooling gas throughput increases with increasing speed of the turbine. Control of the cooling gas flow is thus achieved without any valve means. We can therefore speak of an excellent solution to the problems at hand.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP81101560A 1980-04-15 1981-03-05 Dispositif de refroidissement interne d'une turbine à gaz Withdrawn EP0037897A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3014279 1980-04-15
DE19803014279 DE3014279A1 (de) 1980-04-15 1980-04-15 Einrichtung zur kuehlung des inneren einer gasturbine

Publications (1)

Publication Number Publication Date
EP0037897A1 true EP0037897A1 (fr) 1981-10-21

Family

ID=6099963

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81101560A Withdrawn EP0037897A1 (fr) 1980-04-15 1981-03-05 Dispositif de refroidissement interne d'une turbine à gaz

Country Status (4)

Country Link
EP (1) EP0037897A1 (fr)
JP (1) JPS56151225A (fr)
DE (1) DE3014279A1 (fr)
ES (1) ES264970Y (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0188910A1 (fr) * 1984-12-21 1986-07-30 AlliedSignal Inc. Refroidissement des aubes de turbine
EP0902164A1 (fr) * 1997-09-15 1999-03-17 Asea Brown Boveri AG Refroidissement de la platte-forme dans les turbines à gas
EP0926311A1 (fr) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor pour une turbomachine
EP1396609A3 (fr) * 2002-09-04 2005-05-04 Hitachi, Ltd. Turbine à gaz avec passage de refroidissement délimité par une entretoise et un disque de rotor de turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005025244A1 (de) 2005-05-31 2006-12-07 Rolls-Royce Deutschland Ltd & Co Kg Luftführungssystem zwischen Verdichter und Turbine eines Gasturbinentriebwerks

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1045730B (de) * 1957-12-18 1958-12-04 Maschf Augsburg Nuernberg Ag Einrichtung an metallischen Schaufeltraegern zur Befestigung von Laufschaufeln aus sproeden Werkstoffen, insbesondere fuer Gasturbinen
FR1207772A (fr) * 1957-07-18 1960-02-18 Rolls Royce Perfectionnements aux machines à fluide comportant des rotors à aubes
GB926160A (en) * 1958-12-29 1963-05-15 Gen Electric A gas turbine with preheating and cooling of the turbine rotor
FR1355379A (fr) * 1963-05-07 1964-03-13 Rolls Royce Perfectionnements aux moteurs à turbine à gaz
GB1194663A (en) * 1968-01-10 1970-06-10 Sulzer Ag Hollow Rotors
DE2003947A1 (de) * 1969-01-29 1970-07-30 Gen Electric Gasturbine
DE2047648A1 (de) * 1969-09-29 1971-05-19 Westinghouse Electric Corp Axial Gasturbine der Scheibenbauart
DE2119024A1 (de) * 1970-04-28 1971-11-11 United Aircraft Corp Kühlvorrichtung für Turbinen
DE2147537A1 (de) * 1970-12-18 1972-07-06 Gen Electric Kühleinrichtung für die Enden von Turbinenlaufschaufeln mit Luftexpansion
US3712756A (en) * 1971-07-22 1973-01-23 Gen Electric Centrifugally controlled flow modulating valve
DE2356721A1 (de) * 1972-12-01 1974-06-20 Avco Corp Luftkuehlung von turbinen-schaufeln
DE2357326A1 (de) * 1973-11-16 1975-05-28 Motoren Turbinen Union Turbine mit innenkuehlung des kranzes und sollbruchstellen
DE2805851A1 (de) * 1977-02-18 1978-08-24 Rolls Royce Kuehlsystem fuer turbinen von gasturbinentriebwerken

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1207772A (fr) * 1957-07-18 1960-02-18 Rolls Royce Perfectionnements aux machines à fluide comportant des rotors à aubes
DE1045730B (de) * 1957-12-18 1958-12-04 Maschf Augsburg Nuernberg Ag Einrichtung an metallischen Schaufeltraegern zur Befestigung von Laufschaufeln aus sproeden Werkstoffen, insbesondere fuer Gasturbinen
GB926160A (en) * 1958-12-29 1963-05-15 Gen Electric A gas turbine with preheating and cooling of the turbine rotor
FR1355379A (fr) * 1963-05-07 1964-03-13 Rolls Royce Perfectionnements aux moteurs à turbine à gaz
GB1194663A (en) * 1968-01-10 1970-06-10 Sulzer Ag Hollow Rotors
DE1601664A1 (de) * 1968-01-10 1970-08-06 Sulzer Ag Anordnung fuer den Durchtritt von Gas durch den Mantel eines Rotors
DE2003947A1 (de) * 1969-01-29 1970-07-30 Gen Electric Gasturbine
FR2062769A5 (fr) * 1969-09-29 1971-06-25 Westinghouse Electric Corp
DE2047648A1 (de) * 1969-09-29 1971-05-19 Westinghouse Electric Corp Axial Gasturbine der Scheibenbauart
DE2119024A1 (de) * 1970-04-28 1971-11-11 United Aircraft Corp Kühlvorrichtung für Turbinen
DE2147537A1 (de) * 1970-12-18 1972-07-06 Gen Electric Kühleinrichtung für die Enden von Turbinenlaufschaufeln mit Luftexpansion
US3712756A (en) * 1971-07-22 1973-01-23 Gen Electric Centrifugally controlled flow modulating valve
DE2218705A1 (de) * 1971-07-22 1973-02-01 Gen Electric Durch zentrifugalkraft gesteuertes, stroemungsmodulierendes ventil
DE2356721A1 (de) * 1972-12-01 1974-06-20 Avco Corp Luftkuehlung von turbinen-schaufeln
DE2357326A1 (de) * 1973-11-16 1975-05-28 Motoren Turbinen Union Turbine mit innenkuehlung des kranzes und sollbruchstellen
DE2805851A1 (de) * 1977-02-18 1978-08-24 Rolls Royce Kuehlsystem fuer turbinen von gasturbinentriebwerken
FR2381179A1 (fr) * 1977-02-18 1978-09-15 Rolls Royce Systeme de refroidissement de turbomachines

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0188910A1 (fr) * 1984-12-21 1986-07-30 AlliedSignal Inc. Refroidissement des aubes de turbine
EP0902164A1 (fr) * 1997-09-15 1999-03-17 Asea Brown Boveri AG Refroidissement de la platte-forme dans les turbines à gas
US6082961A (en) * 1997-09-15 2000-07-04 Abb Alstom Power (Switzerland) Ltd. Platform cooling for gas turbines
EP0926311A1 (fr) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor pour une turbomachine
EP1396609A3 (fr) * 2002-09-04 2005-05-04 Hitachi, Ltd. Turbine à gaz avec passage de refroidissement délimité par une entretoise et un disque de rotor de turbine

Also Published As

Publication number Publication date
ES264970U (es) 1982-11-16
DE3014279A1 (de) 1981-10-22
ES264970Y (es) 1983-06-01
JPS56151225A (en) 1981-11-24

Similar Documents

Publication Publication Date Title
DE4447507B4 (de) Ringförmige Dichtung
DE2913548C2 (de) Wellenkühlung für ein Gasturbinentriebwerk
DE3713923C2 (de) Kühlluft-Übertragungsvorrichtung
DE1130646B (de) Diagonalgasturbinen-Energieanlage
DE2541156A1 (de) Verfahren zur aufladung eines verbrennungsmotors, insbesondere eines dieselmotors, und einrichtung zur durchfuehrung des verfahrens
DE2554010A1 (de) Vorrichtung und verfahren zur zufuehrung von kuehlluft zu turbinenleitschaufeln
DE2031612A1 (de) Vielstufiger Axialkompressor mit einem Luftableitsystem als Zwischen stufe
DE2849924A1 (de) Zufuehrung der abgase von einem verbrennungsmotor zum laufrad einer zentripetalturbine eines abgasturboladers
DE1503581B1 (de) Mit Abgasturbo-Aufladung betriebene Zweitakt-Brennkraftmaschine
WO1999063204A1 (fr) Turbine a gaz ainsi que procede pour le refroidissement d'un etage de turbine
DE112012002692B4 (de) Vorrichtung und Verfahren zur Reduzierung des Luftmassenflusses zur emissionsarmen Verbrennung über einen erweiterten Bereich in einwelligen Gasturbinen
DE2628269C3 (de) Gasturbinenanlage für Kraftfahrzeuge, wie Ackerschlepper
WO1998013584A1 (fr) Compensation de la perte de pression d'une conduite d'air de refroidissement dans une installation de turbine a gaz
DE3132134C2 (de) Verfahren und Vorrichtung zur Verminderung des Strömungsquerschnitts für die Auspuffgase im Leitkranz der Turbine eines Abgasturboladers für einen Verbrennungsmotor
DE19652754A1 (de) Abgasturbolader
EP0037897A1 (fr) Dispositif de refroidissement interne d'une turbine à gaz
DE1133184B (de) Gasturbinentriebwerk mit koaxial angeordneten und gegenlaeufig rotierenden Laeufern eines Zentripetal-verdichters und einer Zentrifugalturbine und mit einer Brennkammer
DE3424497C2 (fr)
DE2527871A1 (de) Mehrere arbeitsraeume bildende brennkraftmaschine mit abgasturbolader
EP1117913B1 (fr) Prechauffage du combustible dans une turbine a gaz
DE2154726A1 (de) Radial beaufschlagter abgasturbolader
DE69910052T2 (de) Gasturbine
DE2537308A1 (de) Turbolader-verdichter
DE1751093B2 (de) Gasturbinen triebwerksanlagw
DE2617024A1 (de) Gasturbinentriebwerk

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): AT CH DE FR GB IT NL

ITCL It: translation for ep claims filed

Representative=s name: BARZANO' E ZANARDO MILANO S.P.A.

17P Request for examination filed

Effective date: 19810915

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19830212

RIN1 Information on inventor provided before grant (corrected)

Inventor name: OWSIANNY, EDMUND